Adaptive Fault-Tolerant Control for Attitude Tracking of a Carrier-Based Aircraft Subject to Actuator Faults

• Published in: IEEE transactions on aerospace and electronic systems Vol. 60; no. 5; pp. 6133 - 6145
• Main Authors: Liu, Simin, Zheng, Zewei, Zhu, Bing, Guan, Zhiyuan
• Format: Journal Article
• Language: English
• Published: New York IEEE 01.10.2024; The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
• Subjects: <named-content xmlns:xlink="http://www.w3.org/1999/xlink" xmlns:ali="http://www.niso.org/schemas/ali/1.0/" xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" content-type="math" xlink:type="simple"> <inline-formula> <tex-math notation="LaTeX"> mathcal{L}_{1}</tex-math> </inline-formula> </named-content> adaptive control; Actuators; Adaptation models; Adaptive control; Adaptive sampling; Adaptive systems; Aircraft; Aircraft control; Attitude control; carrier-based aircraft; Closed loops; Data acquisition; Dynamic inversion; Dynamical systems; Fault tolerance; Fault tolerant systems; fault-tolerant control; Faults; Nonlinear control; Nonlinear dynamics; Reference systems; Tracking control
• ISSN: 0018-9251; 1557-9603
• DOI: 10.1109/TAES.2024.3401672

This article presents a fault-tolerant attitude tracking control for carrier-based aircraft subject to actuator faults. The proposed controller adopts nonlinear dynamic inversion (NDI) to ensure asymptotic attitude tracking for the fault-free attitude system and employs <inline-formula><tex-math notation="LaTeX">\mathcal{L}_{1}</tex-math></inline-formula> piecewise constant adaptive law to compensate for errors caused by actuator lock-in-place (LIP) faults. Theoretical analysis indicates that by reducing the sampling time of the adaptive law, the performance difference bounds of the closed-loop <inline-formula><tex-math notation="LaTeX">\mathcal{L}_{1}</tex-math></inline-formula> adaptive system and the closed-loop reference system can be adjusted to be arbitrarily small. The fault-tolerant performance of the proposed method is supported by data acquired from flight tests.